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S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il)
Reynolds number: 200,000
Max Cl/Cd: 59.26 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4094-il-200000.txt
Download as CSV file: xf-s4094-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4094 (root airfoil designed for and used on the
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5710   0.09431   0.09108   0.0075   1.0004   0.0515
  -7.750  -0.5689   0.09008   0.08687   0.0044   1.0004   0.0528
  -7.500  -0.5636   0.08491   0.08171  -0.0010   1.0004   0.0547
  -7.250  -0.5525   0.07354   0.06993  -0.0222   1.0004   0.0591
  -7.000  -0.5455   0.06580   0.06215  -0.0250   1.0004   0.0602
  -6.750  -0.5301   0.06309   0.05952  -0.0241   1.0004   0.0614
  -6.500  -0.5127   0.06090   0.05735  -0.0240   1.0004   0.0639
  -6.250  -0.4875   0.05282   0.04852  -0.0328   1.0004   0.0730
  -6.000  -0.4368   0.03818   0.03448  -0.0329   1.0004   0.0753
  -5.750  -0.4165   0.03490   0.03112  -0.0340   1.0004   0.0783
  -5.500  -0.4024   0.03193   0.02612  -0.0391   1.0004   0.0451
  -5.250  -0.3678   0.02560   0.01866  -0.0404   1.0004   0.0385
  -5.000  -0.3370   0.02355   0.01625  -0.0409   1.0004   0.0381
  -4.750  -0.3073   0.02144   0.01400  -0.0415   1.0004   0.0396
  -4.500  -0.2774   0.02016   0.01259  -0.0420   1.0004   0.0413
  -4.250  -0.2472   0.01873   0.01103  -0.0423   1.0004   0.0421
  -4.000  -0.2172   0.01753   0.00975  -0.0426   1.0004   0.0435
  -3.750  -0.1872   0.01653   0.00870  -0.0429   1.0004   0.0456
  -3.500  -0.1574   0.01551   0.00765  -0.0433   1.0004   0.0486
  -3.250  -0.1276   0.01475   0.00697  -0.0439   1.0004   0.0564
  -3.000  -0.0972   0.01381   0.00615  -0.0445   1.0004   0.0764
  -2.750  -0.0671   0.01285   0.00564  -0.0455   1.0004   0.1604
  -2.500  -0.0380   0.01228   0.00552  -0.0465   1.0004   0.2537
  -2.250  -0.0011   0.01165   0.00557  -0.0492   0.9853   0.4167
  -2.000   0.0354   0.01083   0.00563  -0.0511   0.9545   0.6404
  -1.750   0.0543   0.01026   0.00569  -0.0476   0.9196   0.8484
  -1.500   0.0815   0.00979   0.00514  -0.0463   0.8853   0.9996
  -1.250   0.1070   0.00994   0.00505  -0.0453   0.8579   0.9996
  -1.000   0.1333   0.01010   0.00496  -0.0447   0.8342   0.9996
  -0.750   0.1605   0.01025   0.00490  -0.0442   0.8125   0.9996
  -0.500   0.1879   0.01041   0.00484  -0.0439   0.7933   0.9996
  -0.250   0.2162   0.01055   0.00481  -0.0438   0.7742   0.9996
   0.000   0.2447   0.01070   0.00479  -0.0437   0.7563   0.9996
   0.250   0.2732   0.01086   0.00478  -0.0437   0.7393   0.9996
   0.500   0.3018   0.01101   0.00479  -0.0437   0.7229   0.9996
   0.750   0.3305   0.01117   0.00481  -0.0438   0.7070   0.9996
   1.000   0.3593   0.01133   0.00484  -0.0438   0.6913   0.9996
   1.250   0.3882   0.01149   0.00488  -0.0439   0.6758   0.9996
   1.500   0.4170   0.01165   0.00494  -0.0440   0.6604   0.9996
   1.750   0.4459   0.01181   0.00500  -0.0442   0.6449   0.9996
   2.000   0.4748   0.01197   0.00507  -0.0443   0.6294   0.9996
   2.250   0.5036   0.01214   0.00515  -0.0444   0.6137   0.9996
   2.500   0.5325   0.01232   0.00524  -0.0446   0.5978   0.9996
   2.750   0.5614   0.01248   0.00535  -0.0447   0.5813   0.9996
   3.000   0.5904   0.01264   0.00546  -0.0449   0.5640   0.9996
   3.250   0.6193   0.01281   0.00558  -0.0451   0.5465   0.9996
   3.500   0.6481   0.01299   0.00572  -0.0453   0.5285   0.9996
   3.750   0.6768   0.01319   0.00584  -0.0455   0.5104   0.9996
   4.000   0.7055   0.01339   0.00599  -0.0457   0.4916   0.9996
   4.250   0.7343   0.01359   0.00616  -0.0459   0.4714   0.9996
   4.500   0.7628   0.01383   0.00635  -0.0461   0.4516   0.9996
   4.750   0.7913   0.01410   0.00656  -0.0463   0.4313   0.9996
   5.000   0.8198   0.01438   0.00679  -0.0465   0.4104   0.9996
   5.250   0.8479   0.01473   0.00707  -0.0467   0.3905   0.9996
   5.500   0.8763   0.01505   0.00737  -0.0470   0.3695   0.9996
   5.750   0.9043   0.01542   0.00769  -0.0472   0.3492   0.9996
   6.000   0.9322   0.01583   0.00804  -0.0474   0.3294   0.9996
   6.250   0.9602   0.01622   0.00844  -0.0476   0.3093   0.9996
   6.500   0.9878   0.01667   0.00885  -0.0479   0.2903   0.9996
   6.750   1.0151   0.01716   0.00929  -0.0481   0.2717   0.9996
   7.000   1.0426   0.01762   0.00978  -0.0483   0.2529   0.9996
   7.250   1.0696   0.01814   0.01029  -0.0484   0.2348   0.9996
   7.500   1.0963   0.01871   0.01082  -0.0486   0.2176   0.9996
   7.750   1.1226   0.01935   0.01141  -0.0487   0.2011   0.9996
   8.000   1.1489   0.01994   0.01205  -0.0488   0.1847   0.9996
   8.250   1.1748   0.02059   0.01273  -0.0489   0.1694   0.9996
   8.500   1.2002   0.02132   0.01347  -0.0489   0.1552   0.9996
   8.750   1.2251   0.02210   0.01427  -0.0488   0.1420   0.9996
   9.000   1.2493   0.02295   0.01515  -0.0487   0.1295   0.9996
   9.250   1.2727   0.02388   0.01607  -0.0485   0.1178   0.9996
   9.500   1.2958   0.02473   0.01696  -0.0482   0.1062   0.9996
   9.750   1.3193   0.02543   0.01775  -0.0481   0.0947   0.9996
  10.000   1.3421   0.02619   0.01862  -0.0479   0.0841   0.9996
  10.250   1.3634   0.02713   0.01963  -0.0475   0.0749   0.9996
  10.500   1.3825   0.02829   0.02083  -0.0468   0.0671   0.9996
  10.750   1.4018   0.02933   0.02196  -0.0462   0.0589   0.9996
  11.000   1.4191   0.03054   0.02329  -0.0453   0.0496   0.9996
  11.250   1.4305   0.03230   0.02508  -0.0439   0.0392   0.9996
  11.500   1.4376   0.03434   0.02721  -0.0419   0.0317   0.9996
  11.750   1.4371   0.03683   0.02981  -0.0392   0.0281   0.9996
  12.000   1.4369   0.03895   0.03209  -0.0365   0.0259   0.9996
  12.250   1.4308   0.04147   0.03473  -0.0337   0.0246   0.9996
  12.500   1.4226   0.04476   0.03812  -0.0321   0.0236   0.9996
  12.750   1.4117   0.04884   0.04228  -0.0310   0.0228   0.9996
  13.000   1.4097   0.05222   0.04588  -0.0308   0.0221   0.9996
  13.250   1.4061   0.05595   0.04980  -0.0309   0.0215   0.9996
  13.500   1.4015   0.05990   0.05393  -0.0312   0.0209   0.9996
  13.750   1.3960   0.06408   0.05828  -0.0318   0.0204   0.9996
  14.000   1.3897   0.06846   0.06283  -0.0326   0.0200   0.9996
  14.250   1.3823   0.07306   0.06759  -0.0336   0.0197   0.9996
  14.500   1.3742   0.07787   0.07255  -0.0348   0.0194   0.9996
  14.750   1.3650   0.08292   0.07776  -0.0363   0.0192   0.9996
  15.000   1.3546   0.08826   0.08327  -0.0381   0.0190   0.9996
  15.250   1.3433   0.09389   0.08906  -0.0402   0.0188   0.9996
  15.500   1.3311   0.09988   0.09521  -0.0427   0.0187   0.9996
  15.750   1.3182   0.10628   0.10179  -0.0456   0.0186   0.9996
  16.000   1.3041   0.11325   0.10895  -0.0492   0.0185   0.9996
  16.250   1.2880   0.12101   0.11691  -0.0535   0.0186   0.9996
  16.500   1.2675   0.13019   0.12631  -0.0590   0.0187   0.9996
  16.750   1.2395   0.14193   0.13833  -0.0665   0.0191   0.9996
  17.000   1.1989   0.15823   0.15493  -0.0773   0.0199   0.9996
  17.250   1.0854   0.20534   0.20218  -0.1052   0.0236   0.9996
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